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TECHNICAL PAPERS

Film-Cooled Turbine Endwall in a Transonic Flow Field: Part I—Aerodynamic Measurements

[+] Author and Article Information
Friedrich Kost, Martin Nicklas

Institute of Propulsion Technology, German Aerospace Center (DLR), 37073 Göttingen, Germany

J. Turbomach 123(4), 709-719 (Feb 01, 2001) (11 pages) doi:10.1115/1.1400112 History: Received February 01, 2001
Copyright © 2001 by ASME
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References

Figures

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Oil flow picture of sidewall together with velocity vectors measured by L2F at a wall distance of 0.5 mm, without coolant ejection
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L2F measurements at x/lax=0.10 and at two wall distances (z=0.5 and 20 mm), without coolant ejection; contour Mach number from a profile pressure distribution measurement at z=20 mm
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L2F measurements at x/lax=0.35 and at two wall distances (z=0.5 and 20 mm), without coolant ejection
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L2F measurements at x/lax=0.10 with coolant ejection from the holes only
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L2F measurements at x/lax=0.35 with coolant ejection from the holes only
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L2F measurements at x/lax=0.10 and at the wall distance z=0.5 mm(z/h=0.004); without coolant ejection and with coolant ejection from the slot only
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Coolant concentration from slot ejection at x/lax=0.10
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L2F measurements at x/lax=0.35 and at the wall distance z=0.5 mm(z/h=0.004); without coolant ejection and with coolant ejection from the slot only
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Coolant concentration from slot ejection at x/lax=0.35
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Oil flow picture of the endwall together with velocity vectors measured by L2F at a wall distance of 0.5 mm, with coolant ejection from slot and holes
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Coolant concentration in plane x/lax=0.10 with coolant ejection from slot and holes
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Overview of flow values in plane x/lax=0.35 with coolant ejection from slot and holes
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Overview of flow values in downstream plane x/lax=1.10 with coolant ejection from slot and holes
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Pitch-averaged flow values at x/lax=1.10,Ma2is=1.0
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Area-averaged energy loss values with the area extending from z=2 mm to 30 mm (z/h=0.016 to 0.24); coolant ejection from slot and holes
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Sketch of secondary flow features in a turbine passage according to Langston 4
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Geometry of the stator and the cooling configuration
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Section through cooling geometry (schematic)
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Schlieren picture of flow field in the stator at Ma2is=1.00
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Sidewall boundary layer upstream of cascade
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Isentropic Mach number distribution at the sidewall without coolant ejection (Ma2is=1.00)

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